Busemann进气道起动问题初步研究  

Preliminary investigation on Busemann inlet starting characteristics

作　　者：孙波[1] 张堃元[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2006年第2期128-131,共4页Journal of Propulsion Technology

基　　金：国家"八六三"基金项目(2003AA723020)

摘　　要：为了研究流线跟踪Busemann进气道低马赫数下的起动性能,对设计马赫数Ma1=7,收缩比CR=6的3°截短前后的流线跟踪进气道在Ma=4来流条件下的起动性能进行了无粘数值分析,研究发现：与基准进气道相比,虽然流线跟踪进气道的起动性能显著提高,但它仍不能实现自起动的目标,通过部分切除唇口板的方法将唇口后移,使进气道溢流面积增大,内收缩比减小,并通过逐渐增大切除量的方式,发现3°截短流线跟踪进气道能够自起动的最大参考内收缩比在1.255～1.27之间,并发现在保证该进气道Ma=4自起动的条件下,它在设计状态仍然具有较高的无粘性能.Inviscid flow lations were performed to study the starting characteristics of square streamtraced inlets at Ma = 4 and they are designed for Mach 7 flight and has a same contraction ratio of 6. The results show that streamtraced inlet has a better starting performance than full Busemann inlet, but this inlet is not self-starting yet. In order to realize that 3° truncated streamtraced inlet can be started at take-over Mach number, cut-back of the cowl allow more flow spillage and a reduced internal contraction ratio, it is observed that its maximum reference internal contraction ratio which can be started is between 1. 255 and 1.27. With the inlet self-starting at Ma = 4, it has still high efficiency at design point.

关 键 词：超音速冲压喷机发动机 Busemann进气道^+ 起动 数值仿真 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]